EP0222173B1 - Chambre de combustion pour turbine à gaz - Google Patents

Chambre de combustion pour turbine à gaz Download PDF

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Publication number
EP0222173B1
EP0222173B1 EP86114038A EP86114038A EP0222173B1 EP 0222173 B1 EP0222173 B1 EP 0222173B1 EP 86114038 A EP86114038 A EP 86114038A EP 86114038 A EP86114038 A EP 86114038A EP 0222173 B1 EP0222173 B1 EP 0222173B1
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EP
European Patent Office
Prior art keywords
air
fuel
combustion
bleed
gas turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP86114038A
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German (de)
English (en)
Other versions
EP0222173A1 (fr
Inventor
Nobuyuki Iizuka
Yoji Ishibashi
Isao Sato
Fumiyuki Hirose
Hiroshi Inose
Katsukuni Hisano
Katsuo Wada
Seiichi Kirikami
Michio Kuroda
Yoshihiro Uchiyama
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Hitachi Ltd
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Hitachi Ltd
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Filing date
Publication date
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Publication of EP0222173A1 publication Critical patent/EP0222173A1/fr
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Publication of EP0222173B1 publication Critical patent/EP0222173B1/fr
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/31—Fuel schedule for stage combustors

Definitions

  • the present invention relates to a combustor for supplying working gas of high temperature and high pressure to a gas turbine, and particularly to a gas turbine combustor of two-stage combustion type wherein a gas fuel as natural gas (LNG) is used.
  • LNG natural gas
  • a combustor has a primary fuel nozzle for forming pilot flame at the head of the combustor, a secondary fuel nozzle being provided for supply of premixed air on the downstream side of the flow of combustion gas, and fuel being supplied only to the primary fuel nozzle or to both the primary and secondary fuel nozzles depending on the load of a gas turbine so that low temperature combustion is conducted over the whole range of load of the gas turbine.
  • Such premixed staged combustion has the advantage that the production of nitrogen oxide (NOx) is reduced because the low temperature combustion can be conducted. It also has the problem, however, that secondary fuel is difficult to be burned completely and such un-burned components as CO, HC are exhausted when the fuel begins to be supplied from the secondary fuel nozzle in the process of the gas turbine load's varying from low load to high load.
  • NOx nitrogen oxide
  • a combustor for conducting two-stage combustion it is necessary to regulate and control fuel and air, particularly by supplying secondary fuel, so as to maintain the ratio of air flow rate to fluid flow rate constant in accordance with the load increase and always conduct stable combustion.
  • a combustor having a fuel nozzle so-called a single stage combustor, it has been disclosed in JP-A 45 739/80 that the fuel ratio is maintained constant even though the fuel supply amount changes according to the turbine load.
  • the movable vane is provided close to a secondary fuel nozzle to influence the reliability.
  • Another object of the invention is to provide a gas turbine combustor of two-stage combustion type in which the occurrence of NOx is reduced owing to low temperature diluted combustion at both the first and the second stage to attain high reduction of NOx and stable combustion can be maintained from low load operation to high load operation.
  • the flow rate of premixed air is regulated so as to maintain the ratio of air to fuel constant in accordance with the change of the fuel flow rate corresponding to turbine load, with respect to secondary combustion where the mixture of the air and the fuel premixed before combustion is supplied into a combustor for restraint of the occurrence of NOx. That is, the amount of air introduced to the secondary stage is controlled by bleeding the air effectively only from an air flow passageway to the secondary stage.
  • FIG. 1 illustrates a two-stage combustor to which the present invention is applied, whereby low NOx combustion can be achieved.
  • a gas turbine consists of such major components as a compressor 1, a turbine 2, a combustor 3 and a generator which is not shown.
  • the combustor 3 comprises an inner pipe 4 for defining a combustion chamber, an outer pipe 5 encirculing the inner pipe 4, a casing 7 for defining a cylinder 13 and a tail pipe 8 through which combustion gas is introduced to turbine stator blades 6.
  • Air 11 compressed by the compressor 1 is introduced into the cylinder 13 through a diffuser 12 and further into the inner pipe 4 in the form of combustion air flows 15a, 15b through dilution air holes 14, wall cooling air holes and combustion air openings all formed in the inner pipe 4.
  • the inner pipe 4 is constituted by a front combustion chamber 17 having an inner cylinder cone 16 mounted therein and a rear combustion chamber 18 of a larger diameter than the front combustion chamber.
  • Secondary air supply holes 20 is provided in a connecting section 19 between the front combustion chamber 17 and the rear combustion chamber 18. Fuel is spouted out in the connecting section from secondary fuel nozzles 21 to be fed into the rear combustion chamber 18 together with secondary air 23 so as to form premixed combustion flame 24. Further, apertures 41 (Fig.
  • a pipe line 39 leads from the apertures 41 to connect the same to an exhaust duct 42, to the turbine at a position 43 which is upstream the turbine blades of the second or subsequent stage or a midway stage 44 of the compressor, whereby an air flow rate flowing into a secondary stage is regulated.
  • the air-bleed pipe line 39 is provided with a flow-rate regulating valve 100 which is controlled by a controller 101.
  • ignition of primary fuel 26 spouted from primary fuel nozzles 25 is not shown, primary combustion flame 27 is formed by an ignition plug of piezoelectric compression type.
  • the ignition of the secondary premixed mixture is carried out by applying fire thereto by means of the primary combustion flame 27.
  • the axes of abscissas indicate the gas turbine load and the axes of ordinate respectively exhibit the secondary fuel ration, the air flow rate and the fuel flow rate.
  • the combustor of two-stage combustion is operated with primary fuel G from the ignition to about 25% rate of the gas turbine load, and the primary fuel is reduced as shown by G' when the gas turbine load has reached 25% rate while secondary fuel H' is supplied simultaneously. Subsequently, the primary and secondary fuels G, H are gradually increased for a rise of the load.
  • the air flow rate is increased corresponding to a rise of the rotational speed of the turbine, until the generator reaches a synchronous speed or while the gas turbine is operated with no-load, but the air flow rate becomes constant when the gas turbine is operated with load so that both of the primary and secondary air flow rate C D are constant.
  • the weight ratio of the secondary fuel to the air is shown in Fig. 2(a). In Fig.
  • the air flow rate is controlled as shown by the F line of Fig. 2(b) with the air flow to the two-stage being bled after the supply of the secondary fuel. More specifically, the controller 101 in Fig. 1 receives load signals of the gas turbine and controls the amount of bleed air in accordance with the load as shown by the solid line in Fig. 3. The amount of bleed air is controlled by changing the extent to which the valve 100 is opened. Then, the ratio of the secondary fuel to the air results in the solid line B and is within the range X where the production of NOx is reduced and the combustion state is preferable so that the stable combustion can be maintained.
  • Secondary fuel and air supply means are provided at the connecting section 19 of the front combustion chamber 17 and the rear combustion chamber 18.
  • the fuel is first introduced from a plurality of secondary fuel introducing portions 28 into respective reservers 29 to be injected from a plurality of spouting holes 31 which open at the top ends of a plurality of secondary fuel nozzles 21 and be mixed with a secondary air flow 32.
  • a swirler 33 which constitutes a mixing chamber, they are changed into a premixed mixture and introduced into the rear combustion chamber 18 to form premixed flame.
  • Air flow 34 flowing between the inner pipe 4 and the outer pipe 5 branches into primary combustion air flow 35 and secondary combustion air flow 36. After the secondary air flow 36 passes through the combustion air holes 20, it branches into flow 32 toward the rear combustion chamber 18 and air flow 37 to be bled.
  • the bleed air flow 37 is expelled into exhaust gas or the atmosphere while being regulated by way of the air-bleed valve 100 from air-bleed openings 41 through passageways 38 and the pipe line 39.
  • the air flow 37 may be introduced to the turbine at a position which is upstream the turbine blades of the second or subsequent stage on the midway stage 44 (Fig. 1) of the compressor.
  • the air-bleed openings 41 are provided to open in the passageway from the combustion air holes 20 to the fuel nozzles 21.
  • each air-bleed opening 41 is located in close proximity of the swirler 33 because the mixture is sometimes bled simultaneously with the bleed of air so that the fuel is also discharged out of the system. Also, it is not preferable that the openings are located on the upstream side of the air holes 20 because a part of the combustion air 35 to be introduced into the primary stage is also bled.
  • Fig. 5 shows a modification wherein the air-bleed openings are provided on the reverse side as compared with those in the embodiment of Fig. 4 or the side of the rear combustion chamber 18 relative to the second combustion air holes 20.
  • the secondary air flow regulating function of this modification is substantially the same as the first embodiment.
  • Fig. 3 shows the bleed air rate according to the invention in comparison with that according to the prior art.
  • This figure represents a case where the secondary fuel is supplied from the point of 25% of the load, and the present invention is illustrated by the solid line and the prior art is by the dotted line.
  • it is necessary to reduce the secondary air flow rate to about half of that at the time of rated load upon supplying of the secondary fuel so that the secondary fuel may be supplied to be mixed with the secondary air and then ignited to be burned completely.
  • the air flow rate for secondary combustion at the time of rated load is about 30% of the overall air flow rate, it is required to reduce the secondary air flow rate to 15% when the secondary fuel is supplied.
  • the present invention therefore, it is necessary to bleed approximately 15% of the whole air flow rate. If such an effect as mentioned above is attempted to be attained by the known art, all the air rate must be reduced to half level in order to decrease only the secondary air amount from the overall air. Then, it is required to bleed about 45% of the air even if it is taken into account that the gas turbine load is covered by the increase of the fuel flow rate compensating the decrease of the air amount. In this way, according to the prior art, the bleed air amount is required about three times so as to reduce the secondary air flow rate to half.
  • the occurrence of NOx at the primary stage is increased because the fuel ratio in the primary combustion becomes large due to 45% decrease of the overall air amount, and the balance of the combustion air distribution is broken since the amount of air flow for cooling the inner pipe of the combustor is reduced.
  • the turbine efficiency is decreased because the amount of bleed air is increased.
  • the turbine efficiency decreases owing to an increase of the fuel flow rate, and the whole efficiency of the turbine is decreased by about 0.3% responsively to the air bleeding from the overall air flow at 1% rate thereof. Accordingly, the turbine efficiency in the invention is decreased by about 5% in contrast to the decrease of about 13% in case of.
  • Fig. 6 another embodiment wherein the bleed air amount 48 may be further reduced by attaching a covering 47 which is capable of changing the opening area of each secondary combustion air hole 20 gradually.
  • Fig. 7 shows a result of the case where the combustor is operated to reduce the opening area of each air hole 20 under the operating condition in which the bleed air amount 48 is large, and to increase the opening area of each air hole 20 by sliding the covering 47 when the bleed amount is small.
  • the case where the opening area is adapted to be phasedly changeable is shown by the solid line and the case where only the air-bleeding is carried out is represented by the dotted line.
  • the opening areas are controlled so as to open continuously or intermittently in accordance with the increase of load over than 25% of load, as shown by the solid line in Fig. 7, the bleed air amount and the fuel flow rate are reduced and the thermal efficiency is increased to result in further improvement of the efficiency of the combustor. That is, when the opening area is reduced by about 50%, the bleed air amount is reduced to about half and the decrease of thermal efficiency is reduced by half. Therefore, a sufficient result can be attained when both the air-bleeding method and the method of changing the opening areas are employed. In this case, the control of the opening areas of the air holes 20 by the covering 47 may be rough and thus, a design may be made giving priority to the reliability.
  • a performance can be obtained at the approximately same degree as the prior art by regulating and controlling the opening areas of the air holes to reduce the bleed air amount to about 1/3 as compared that of the prior art.
  • the decrease of the turbine efficiency resulted from the air-bleeding can be suppressed to a minimum by controlling only secondary air flow rate.
  • Figs. 8 and 9 show a case where the secondary air flow rate is regulated by bleeding the air and a case where the secondary air flow rate is not regulated, respectively, and in these figures the axes of ordinate and abscissa are indicated at the same scale.
  • Fig. 8 shows the case where the air flow rate is not regulated.
  • the experiment is conducted under the actual loading condition of a 70 MW class gas turbine plant and the result is indicated in Fig. 8.
  • the emission of nitrogen monoxide CO, hydrocarbon HC which are un-burned components is increased after the supplying of secondary fuel.
  • the amount of the air flow for forming the premixed mixture is reduced since the secondary air flow is exhausted by bleeding a part thereof when the secondary fuel is supplied, and the condition that the air is slightly in excess of a small amount of fuel can be maintained so that the un-burned components as shown in Fig. 8 are scarcely exhausted.
  • the combustion of high efficiency in which the production of NOx is reduced and the occurrence of the un-bumed components is restrained can be conducted over a wide range from the supplying of the secondary fuel to the rated load operation, by bleeding the secondary air flow at the time of the supply of the secondary fuel and subsequently controlling the air flow rate for reduction of the bleed air rate in accordance with the increase of the fuel.
  • Fig. 10 shows a relation between bleed air rate, and NOx and CO according to the prior art disclosed in JP-A 45 739/80.
  • An experimental result at the time of gas turbine load of 25% rate is shown in Fig. 10.
  • the bleed air amount the air bleed is carried out from the overall combustion air
  • the density of CO which is an un-burned component is not reduced and the effect is not satisfactory.
  • the air-bleed is effected on the overall air amount for reduction of the secondary combustion air.
  • the overall air flow amount is required to be reduced to half so that the flow amount of the secondary air which corresponds to about 25% of the overall air flow amount may be reduced to about half, the efficiency of the secondary combustion cannot be improved unless a great amount of air is bled.
  • the combustion in the primary stage changes to a high-temperature condition wherein the fuel is too rich, because the overall air amount is reduced by the air bleed to decrease particularly the air flow to the primary stage. For this reason, there exists a disadvantage that the occurrence of NOx at the primary stage is increased.
  • Fig. 11 is a characteristic diagram of NOx and CO shown at the same scale as Fig. 10, and represents the result according an embodiment of the present invention in which air is bled from a secondary air passage. As seen in the figure, the secondary combustion efficiency is improved by a small amount of bleed air and the density of NOx in the exhaust can be reduced.
  • Fig. 12 shows still another embodiment of the invention, in which each air-bleed hole is separated into two sections that are respectively provided on the left and right sides of each secondary combustion air hole 20.
  • the improvement of the secondary combustion efficiency can be attained with about one third of the bleed air amount as compared with the case where the air is bled from the overall air in a combustor as shown in the prior art.
  • the change of the characteristics of the primary combustion does not occur and desirable combustion can be maintained, because the balance of the primary and overall air flow amount distribution is not broken. Therefore, a large reduction of NOx can be achieved over a wide range from ignition to the rated load without lowering the combustion efficiency.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)

Claims (2)

1. Brûleur pour turbine à gaz comportant une chambre de combustion primaire (17) qui inclut au moins une buse primaire (25), qui débouche dans cette chambre et par l'intermédiaire de laquelle un combustible est envoyé en permanence pendant le fonctionnement d'une turbine à gaz (1, 2), une chambre de combustion secondaire (18) prévue sur le côté aval de ladite chambre de combustion primaire (17), par rapport à l'écoulement des gaz de combustion, et incluant, sur sa paroi circonférentielle, des trous (20) de passage de l'air secondaire, servant à envoyer de l'air pour le mélange préalable de l'air de combustion secondaire au combustible délivré par au moins une buse secondaire (21) de délivrance du combustible, en vue de délivrer le mélange, et un conduit arrière (8) introduisant les gaz de combustion produits dans lesdites deux chambres de combustion (17, 18) dans la turbine à gaz, le combustible étant délivré uniquement par la buse primaire (25) de délivrance du combustible pour réaliser la combustion uniquement dans la chambre de combustion primaire (17) dans les conditions de fonctionnement, dans lesquelles la charge de la turbine à gaz est à un niveau faible prédéterminé et le combustible est délivré respectivement à partir desdites buses (25, 21) de délivrance du combustible pour l'obtention de la combustion dans les deux chambres de combustion (17, 18), dans les conditions de fonctionnement, dans lesquelles la charge de la turbine à gaz est à un niveau élevé prédéterminé, caractérisé en ce qu'il est prévu des moyens de purge d'air (38, 39, 41, 100, 101) servant à purger une partie de l'air de combustion secondaire seul, et lesdits moyens de purge d'air sont adaptés de manière à purger l'air dans les conditions de fonctionnement, dans lesquelles le combustible secondaire est délivré et la charge de la turbine à gaz est supérieure au niveau bas prédéterminé et inférieure au niveau élevé prédéterminé.
2. Brûleur pour turbine à gaz selon la revendication 1, caractérisé en ce que lesdits moyens de purge d'air incluent une soupape de régulation (100) servant à régler le débit de l'air de purge et un dispositif de commande (101) servant à commander ladite soupape de régulation (100), et commandent le débit de l'air de purge de sorte que ce débit peut être rendu maximum pour la valeur minimale de la charge, pour laquelle le combustible secondaire est délivré, et peut être réduit en fonction d'un accroissement de la charge à partir de ladite valeur, de manière à être amené à zéro au moment de la charge complète.
EP86114038A 1985-10-11 1986-10-10 Chambre de combustion pour turbine à gaz Expired EP0222173B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP22474785 1985-10-11
JP224747/85 1985-10-11

Publications (2)

Publication Number Publication Date
EP0222173A1 EP0222173A1 (fr) 1987-05-20
EP0222173B1 true EP0222173B1 (fr) 1990-03-21

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EP86114038A Expired EP0222173B1 (fr) 1985-10-11 1986-10-10 Chambre de combustion pour turbine à gaz

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US (1) US4766721A (fr)
EP (1) EP0222173B1 (fr)
JP (1) JPH0663646B2 (fr)
DE (1) DE3669750D1 (fr)

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Also Published As

Publication number Publication date
EP0222173A1 (fr) 1987-05-20
US4766721A (en) 1988-08-30
JPS62175524A (ja) 1987-08-01
DE3669750D1 (de) 1990-04-26
JPH0663646B2 (ja) 1994-08-22

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